EP1568795B1 - Superalliage résistant à la chaleur et son utilisation - Google Patents

Superalliage résistant à la chaleur et son utilisation Download PDF

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Publication number
EP1568795B1
EP1568795B1 EP20040024768 EP04024768A EP1568795B1 EP 1568795 B1 EP1568795 B1 EP 1568795B1 EP 20040024768 EP20040024768 EP 20040024768 EP 04024768 A EP04024768 A EP 04024768A EP 1568795 B1 EP1568795 B1 EP 1568795B1
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EP
European Patent Office
Prior art keywords
content
hafnium
alloy
lanthanum
titanium
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
EP20040024768
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German (de)
English (en)
Other versions
EP1568795A1 (fr
Inventor
Gerald Schall
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BorgWarner Inc
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BorgWarner Inc
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Publication date
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Priority to EP20040024768 priority Critical patent/EP1568795B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2203/00—Non-metallic inorganic materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds

Definitions

  • the present invention relates to a heat-resistant superalloy, particularly to a nickel-based one.
  • Such alloys are used in turbines for a variety of components, but also for other purposes, such as parts of ovens and devices to be installed in ovens.
  • the invention also relates to a particular use of this superalloy.
  • alloys for similar purposes are known in numerous forms, such as the U.S. Patent Nos. 3,466,171 ; 4,236,921 JP-A-11131162 or 5,439,640 evident.
  • alloy marketed under the designation MAR 247 LC which is particularly used for achieving higher vibration resistance on turbine wheels and consists of eleven elements, including a large proportion of cobalt, but also a relatively large proportion of tantalum and Hafnium is located. This makes this alloy relatively inexpensive.
  • this alloy has no cobalt and only small amounts of tantalum and hafnium and is therefore less expensive than before. It allows directional solidification, is resistant to breakage of grain boundaries during casting, is also suitable for thin wall thicknesses, and exhibits an improved carbide microstructure, improved carbide stability, and, most importantly, a relatively high ductility over the prior art.
  • the traces of tantalum should be below 2% by weight, preferably below 1.5% by weight, in particular below 1% by weight.
  • the ⁇ '-formation Ni3 is due to the proportions of aluminum and titanium, which preferably together make up a proportion of> 7 wt .-%.
  • the proportion of aluminum serves a dual purpose, namely on the one hand to form the ⁇ '-phase of nickel and on the other hand to obtain a long-term corrosion protection, because it forms a protective layer of Al 2 O 3 on the surface, which at high temperatures, in particular the Turbocharger of a turbocharger driving exhaust gas, is particularly effective.
  • the elements Ti, Nb and Al are responsible for the precipitation hardening and the intermetallic compound, the latter being particularly dense in the alloy according to the invention. These three elements together should therefore be preferred together have a larger proportion than 9.5 wt .-%.
  • the precipitation hardening achieves a higher level of nominal strength, so that the material matrix has to endure less plastic than elastic thermodynamic oscillation amplitudes and thus also achieves a higher resistance to vibration.
  • hafnium and lanthanum contribute to this.
  • hafnium and lanthanum which in this case has a multiple and synergetic function
  • the content of hafnium and lanthanum together amounts to a maximum of 0.7% by weight.
  • the lanthanum content will be at least 0.0035 wt .-% and will advantageously not exceed 0.015 wt .-%, preferably not more than 0.01 wt .-%.
  • the hafnium content should be at least 0.3% by weight and advantageously at most 0.7% by weight, preferably at most 0.6% by weight.
  • the element hafnium is incorporated into the ⁇ '-phase of nickel, thereby increasing its strength.
  • the hafnium content also reduces hot cracking during the casting of the alloy, especially for materials with columnar dendrites (stem grains).
  • Elements B and Zr improve creep strength, creep rupture strength and ductility (to which several elements of this alloy contribute) by grain boundary cohesion. Both elements prevent the formation of carbide films on the grain boundaries. However, these elements are only to be introduced in such tracks to the grain boundaries saturate. Therefore, it is preferable that the content of boron is between 0.01 and 0.035 wt% and / or the content of zirconium is between 0.02 and 0.08 wt%.
  • the element niobium substitutes the aluminum in the ⁇ 'phase and thereby increases the ⁇ ' content in a desired manner.
  • low-cycle fatigue fatigue is strongly influenced by the fineness of the ⁇ 'phase, and it is now the niobium element which effectively counteracts ⁇ ' coarsening
  • the matrix according to the invention also has the role of a mixed crystal former.
  • the alloy in environments up to 900 ° C is free from the formation of a sigma phase. This, together with the improved low-cycle fatigue, makes the alloy of the invention particularly suitable for use with turbine wheels, in particular turbochargers.
  • Fig. 1 is a microsection of an alloy according to the later discussed Example 1 to see.
  • the surface of the alloy with the corrosion-protective Al 2 O 3 layer is not visible in this figure.
  • this alloy thus had a total content of tungsten and molybdenum of 15 wt .-% and a total content of aluminum and titanium of 8 wt .-%, wherein the sum of the contents of titanium, niobium and aluminum 10 wt. -% mattered.
  • the content of hafnium and lanthanum accordingly made up 0.41% by weight, that is to say far below the maximum content and even below the preferred maximum value of 0.7% by weight.
  • the corrosion resistance was tested in a hot gas test and this showed a micrograph under the scanning electron microscope with a clear aluminum layer on the surface, which oxidized to Al 2 O 3 and thus provided a corrosion protection layer. This micrograph also clearly indicated the saturation of the grain boundaries by boron and zirconium. Neither dendrites nor columnar crystals were formed; rather, a fairly uniform grain was found, as one might wish (cf. Fig. 1 )
  • a second alloy having the following composition (in% by weight) was used to form the remainder of nickel: C Cr al Ti Not a word W Nb B Zr Hf La 0.09 9.5 5.5 2.5 2 13 1.75 0,025 0.08 0.45 0.005
  • this alloy thus had a total content of hafnium and lanthanum of 0.455 wt .-%, a total content of tungsten and molybdenum of 15 wt .-% and a total content of aluminum and titanium of 8 wt .-%, wherein the sum of the contents of titanium, niobium and aluminum was 9.75% by weight. So no tantalum was used here.
  • Example 1 The thus formed alloy was then subjected to the same tests as in Example 1, whereby the elasticity was slightly improved over Example 1.
  • a third alloy having the following composition (in% by weight) was used to form the remainder of nickel: C Cr al Ti Not a word W Nb B Zr Hf La Ta 0.12 8.5 4.5 3.5 2.75 11.5 2.3 0.01 0.03 0.6 0,004 0.6
  • this alloy thus had a nickel content of 65.586 wt .-%. It should be noted that this alloy thus had a total content of hafnium and lanthanum of 0.604 wt .-%, a total content of tungsten and molybdenum of 15 wt .-% and a total content of aluminum and titanium of 8 wt .-%, wherein the sum of the contents of titanium, niobium and aluminum was 10% by weight.
  • Example 1 The tests carried out as in Example 1 gave a slightly increased ductility. However, when an endurance test in a corrosive atmosphere (combustion gases of a gasoline engine at about 900 ° C) was carried out, a somewhat reduced corrosion resistance was exhibited as compared with a similar test of the samples of Examples 1 and 2.
  • this alloy thus had a total content of hafnium and lanthanum of 0.82 wt .-%, a total content of tungsten and molybdenum of 12 wt .-% and a total content of aluminum and titanium of 8 wt .-% , wherein the sum of the contents of titanium, niobium and aluminum made up 9.5 wt .-%. Again, they had dispensed with the addition of tantalum.
  • turbocharger turbine rotors were also prepared which were first subjected to solution annealing at 1200 ° C for 8 hours and then precipitation hardening at 860 ° C for 16 hours, each time with subsequent air cooling. All test rotors were subjected to a long-term test and proved to be above expectations.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)

Claims (10)

  1. Superalliage réfractaire qui satisfait les conditions suivantes : - carbone 0,01 - 0,2 % en poids - chrome 8 - 10 % en poids - aluminium 4 - 6 % en poids - titane 2 - 4 % en poids - molybdène 1,5 - 2,8 % en poids - tungstène 10 - 13,5 % en poids - niobium 1,5 - 2,5 % en poids - bore 0 < B ≤ 0,04 % en poids - zirconium 0 < Zr ≤ 0,15 % en poids
    - la somme des teneurs en hafnium et lanthane vaut 0 < Hf + La ≤ 1,5 % en poids,
    - éventuellement moins de 2 % en poids de traces de tantale,
    - le reste étant constitué de nickel.
  2. Superalliage selon la revendication 1, caractérisé en ce que la teneur en bore satisfait au moins l'une des conditions suivantes :
    (a) elle est d'au moins 0,01 % en poids,
    (b) elle est d'au plus 0,035 % en poids.
  3. Superalliage selon les revendications 1 ou 2, caractérisé en ce que la teneur en zirconium satisfait au moins l'une des conditions suivantes :
    (a) elle est d'au moins 0,02 % en poids,
    (b) elle est d'au plus 0,08 % en poids.
  4. Superalliage selon l'une des revendications précédentes, caractérisé en ce que la teneur en lanthane satisfait au moins l'une des conditions suivantes :
    (a) elle est d'au moins 0,0035 % en poids,
    (b) elle est d'au plus 0,015 % en poids et de préférence d'au plus 0,01 % en poids.
  5. Superalliage selon l'une des revendications précédentes, caractérisé en ce que la somme des teneurs en hafnium et lanthane est d'au plus 0,7 % en poids et en ce que le superalliage satisfait de préférence les conditions supplémentaires suivantes :
    (a) la teneur en hafnium est d'au moins 0,3 % en poids,
    (b) la teneur en hafnium elle est d'au plus 0,7 % en poids et de préférence d'au plus 0,6 % en poids.
  6. Superalliage selon l'une des revendications précédentes, caractérisé en ce que la somme des teneurs en tungstène et molybdène est supérieure ou égale à 14 % en poids.
  7. Superalliage selon l'une des revendications précédentes, caractérisé en ce que la somme des teneurs en aluminium et titane est supérieure ou égale à 7 % en poids.
  8. Superalliage selon l'une des revendications précédentes, caractérisé en ce que la somme des teneurs en titane, niobium et aluminium est supérieure ou égale à 9,5 % en poids.
  9. Superalliage selon l'une des revendications précédentes, caractérisé en ce que la teneur en tantale est inférieure à 2 % en poids, de préférence inférieure à 1,5 % en poids et en particulier inférieure à 1 % en poids.
  10. Utilisation d'un alliage selon l'une des revendications précédentes pour le moulage d'aubes de turbines et en particulier de turbocompresseurs.
EP20040024768 2003-11-20 2004-10-18 Superalliage résistant à la chaleur et son utilisation Expired - Fee Related EP1568795B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20040024768 EP1568795B1 (fr) 2003-11-20 2004-10-18 Superalliage résistant à la chaleur et son utilisation

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP03026683 2003-11-20
EP03026683 2003-11-20
EP20040024768 EP1568795B1 (fr) 2003-11-20 2004-10-18 Superalliage résistant à la chaleur et son utilisation

Publications (2)

Publication Number Publication Date
EP1568795A1 EP1568795A1 (fr) 2005-08-31
EP1568795B1 true EP1568795B1 (fr) 2008-04-30

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EP20040024768 Expired - Fee Related EP1568795B1 (fr) 2003-11-20 2004-10-18 Superalliage résistant à la chaleur et son utilisation

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US (2) US20050238526A1 (fr)
EP (1) EP1568795B1 (fr)
JP (1) JP4583894B2 (fr)
DE (1) DE502004006994D1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101300368B (zh) * 2005-09-15 2011-08-31 格瑞得有限责任公司 高硅铌铸造合金及其生产方法
US7824606B2 (en) * 2006-09-21 2010-11-02 Honeywell International Inc. Nickel-based alloys and articles made therefrom
US8118556B2 (en) 2007-01-31 2012-02-21 Caterpillar Inc. Compressor wheel for a turbocharger system
DE112009002098T5 (de) * 2008-09-25 2011-07-28 BorgWarner Inc., Mich. Turbolader und Baugruppe zur Bypassregelung im Turbinengehäuse dafür
US8858873B2 (en) 2012-11-13 2014-10-14 Honeywell International Inc. Nickel-based superalloys for use on turbine blades
DE102013210990A1 (de) * 2013-06-13 2014-12-18 Continental Automotive Gmbh Abgasturbolader mit einem Radial-Axial-Turbinenrad
KR101669440B1 (ko) * 2014-12-24 2016-10-26 재단법인 포항산업과학연구원 니켈 크롬계 리본 섬유 및 그 제조방법
CA3052705A1 (fr) * 2017-02-24 2018-08-30 The Board Of Regents Of The University Of Texas System Compositions et methodes associees a une fusion de cellule musculaire favorisee par la proteine myomixer
US10933469B2 (en) 2018-09-10 2021-03-02 Honeywell International Inc. Method of forming an abrasive nickel-based alloy on a turbine blade tip

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3888663A (en) * 1972-10-27 1975-06-10 Federal Mogul Corp Metal powder sintering process
US4078951A (en) * 1976-03-31 1978-03-14 University Patents, Inc. Method of improving fatigue life of cast nickel based superalloys and composition
US4907947A (en) * 1988-07-29 1990-03-13 Allied-Signal Inc. Heat treatment for dual alloy turbine wheels
JP3812773B2 (ja) * 1997-10-27 2006-08-23 日立金属株式会社 Ｎｉ基超耐熱鋳造合金およびＮｉ基超耐熱合金製タービンホイール
JP4811841B2 (ja) * 2001-04-04 2011-11-09 日立金属株式会社 Ｎｉ基超耐熱鋳造合金およびＮｉ基超耐熱合金製タービンホイール

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JP4583894B2 (ja) 2010-11-17
US20080271822A1 (en) 2008-11-06
EP1568795A1 (fr) 2005-08-31
US20050238526A1 (en) 2005-10-27
US9051844B2 (en) 2015-06-09
JP2005171384A (ja) 2005-06-30
DE502004006994D1 (de) 2008-06-12

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